Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from a first scanner; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; and commanding, via the processor, a contact probe to perform a non-destructive inspection on the areas of interest.

Abstract: An inspection device is disclosed herein. In various embodiments, the inspection system device comprises: a support structure; a motor, a shaft operably coupled to the motor, the shaft extending from a first side of the support structure to a second side of the support structure, the shaft configured to couple to a bladed rotor; and a scanner moveably coupled to the support structure, the scanner configured to generate a three-dimensional model for the bladed rotor.

Abstract: A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values.

Abstract: A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections.

Abstract: A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections.

Abstract: A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values.